EP3560827B1 - Undercarriage provided with a lithgning protection device - Google Patents

Undercarriage provided with a lithgning protection device Download PDF

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Publication number
EP3560827B1
EP3560827B1 EP19170692.8A EP19170692A EP3560827B1 EP 3560827 B1 EP3560827 B1 EP 3560827B1 EP 19170692 A EP19170692 A EP 19170692A EP 3560827 B1 EP3560827 B1 EP 3560827B1
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EP
European Patent Office
Prior art keywords
plate
undercarriage
electrical equipment
undercarriage according
metal
Prior art date
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EP19170692.8A
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German (de)
French (fr)
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EP3560827A1 (en
Inventor
Jérôme GUI
Alexandre AVENET
Pierre PIZANA
Yvain SERIGNAC
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Safran Landing Systems SAS
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Safran Landing Systems SAS
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Publication of EP3560827A1 publication Critical patent/EP3560827A1/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/02—Lightning protectors; Static dischargers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/405—Powered wheels, e.g. for taxing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management

Definitions

  • the present invention relates to the field of aeronautics and more particularly to aircraft landing gear.
  • aircraft Since the risk of an aircraft being struck by lightning is quite high, aircraft include a certain number of means making it possible to limit the consequences of a lightning strike.
  • the structural elements of the aircraft are therefore connected to the ground of the aircraft and the equipment liable to be struck by lightning is protected by lightning rods.
  • the equipment currently installed on the landing gear is not threatened so that no protection against lightning is provided.
  • the geared motor has parts that are sufficiently spaced apart from the leg of the undercarriage to promote a peak effect so that said parts would constitute privileged lightning strike zones. Such a lightning strike could destroy the gear motor and transmit strong currents and high voltages to the electrical and/or electronic devices to which the gear motor is connected. A risk of fire in the fuselage cannot be ruled out either.
  • EP 2 735 850 A2 describes a lower part of an aircraft landing gear comprising a sensor arranged inside a free end of an axle. Conductive fingers extend radially from the sensor and contact an inner surface of the axle to form a low impedance path between the axle and the sensor to prevent damaging arcing due to e.g. to a lightning strike at the nose of the aircraft.
  • An object of the invention is to provide a means for limiting the risk that a lightning strike will permanently alter the operation of an aircraft.
  • an aircraft undercarriage comprising electrical equipment fixed to a part of the undercarriage and an anti-lightning device comprising at least one shield fixed to said part of the undercarriage by fastening means to extend facing the electrical equipment in a position spaced from the latter.
  • the shield comprising at least a first plate made of electrically conductive material arranged to absorb a major part of a thermal energy generated by a passage of a lightning wave and to evacuate the electric charges of the lightning wave.
  • the first plate is therefore intended to form the point of entry or exit of the lightning wave and to evacuate the currents as easily as possible. correspondents.
  • the first phase of the lightning wave being very powerful with very high frequencies, the currents do not enter the first plate and essentially circulate on the surface of the first plate.
  • the second phase of the lightning wave is very energetic, the currents enter the plate and the thermal stress is absorbed by the first plate.
  • the first plate is preferably made of a material that is fusible at the temperature generated by the passage of the lightning wave so that it will melt at least in part. The distance left between the first plate and the electrical equipment makes it possible to limit the risk of excessive heating of the electrical equipment.
  • the anti-lightning device comprises a second plate of electrically conductive material extending parallel to the first plate between the latter and the electrical equipment in a position separated from the electrical equipment and the first plate.
  • the first plate is fixed to the second plate which forms part of the means for fixing the first plate to said part of the undercarriage, the second plate being connected to the electrical equipment.
  • the second plate supports the first plate, ensures the continuity of the currents towards the structure of the undercarriage and constitutes a second thermal insulation. If the first plate is made of metal, the second plate blocks any projections of molten metal coming from the first plate. The electrical equipment is therefore protected from high currents, splashes of molten metal and localized temperature rise at the point of entry or exit of the lightning wave.
  • the invention also relates to an aircraft equipped with such a landing gear.
  • the invention is described in application to an aircraft 50 comprising a fuselage 51 containing an electronic control unit 52 of the aircraft 50.
  • the fuselage 51 comprises a nose provided with a landing gear generally designated 100.
  • the undercarriage 100 comprises a leg 1 having an end 1.1 hinged to the fuselage 51 and a free end 1.2 provided with two axles 101 each to receive a wheel 102.
  • the free end 1.2 is also provided with an electric gear motor 2 intended to drive in rotation the wheels 102 and connected by a harness 3 of electric cables to a power source, not shown, and to the control unit 52.
  • the geared motor 2 is arranged to mesh with a toothed wheel connected in rotation with one of the wheels 102 in such a way that the control of the geared motor 2 allows the driving of the wheel 102 in rotation during taxiage maneuvers.
  • the harness 3 extends in a cable tray which runs along the leg 1 of the undercarriage 100.
  • the undercarriage 100 is known in itself and will not be further detailed. here. In particular, the deployment and retraction means of the undercarriage 100 are not shown, nor are the means for engaging the geared motor on the toothed wheel and disengaging it therefrom.
  • the lander 100 comprises an anti-lightning device, generally designated at 10, comprising several shields fixed to the free end 1.2 of the leg 1 of the lander by fastening means in such a way that the shields extend opposite of the geared motor 2 and of the lower section of the beam 3. Each shield extends in a spaced position from the geared motor 2 or from the lower section of the beam 3 opposite which it is positioned.
  • Each shield comprises a first plate 11 and a second plate 12.
  • the first plate 11 is made of electrically conductive material and is arranged to absorb a major part of a thermal energy generated by a passage of a lightning wave and to evacuate the electric charges of the lightning wave.
  • the first plate 11 is made of metal and has a thickness between approximately 2 and 4 mm.
  • the metal of the first plate 11 is here an aluminum.
  • the second plate 12 is made of electrically conductive material.
  • the second plate 12 is made of metal and has a thickness between approximately 1 and 2 mm.
  • the metal of the second plate 12 is here an aluminum or a steel.
  • the first plate 11 is fixed by columns on the second plate 12 which forms part of the means for fixing the first plate 11 to the free end 1.2 of the leg 1 of the undercarriage. These columns are each formed of a steel or aluminum bolt extending into a tubular spacer which is clamped between the two plates to hold them apart the two plates from each other.
  • the second plate 12 extends parallel to the first plate 11 between the latter and the geared motor 2 and the beam 3 in a spaced position from the geared motor 2 and from the beam 3 and from the first plate 11.
  • the first plate 11 is separated from the second plate 12 by a distance between approximately 3 mm and 5 mm.
  • the means for fixing the shields extending opposite the bundle 3 connect the second plate 12 to the cable tray by columns. These columns are each formed of a steel or aluminum bolt extending in a tubular spacer holding apart the second plate and the cable tray.
  • the means for fixing the shields extending opposite the geared motor 2 here also comprise two side walls 13, 14 made of electrically conductive material which connect the second plate 12 to the free end 1.2 and extend on either side of the gearmotor 2 at a distance from it.
  • the shield may only comprise a single plate, namely the first plate.
  • the first plate will then have a greater thickness in order to be able to absorb the thermal energy generated by the passage of the lightning wave. This is particularly important in the case where the first plate is made of metal: it is necessary to prevent the first plate from being pierced and molten metal from being projected onto the electrical equipment.
  • Electrical equipment can be any item that conducts electricity, an electrical harness, a electromagnetic or electromechanical actuator, a power circuit or a control circuit...
  • the side walls 13, 14 can be provided with openings to allow air circulation promoting cooling of the electrical equipment.
  • the shield can be installed on any type of train and for example on a two-street train or on a bogie train with four or six wheels.
  • the actuator and the connection to the wheel of the taxiing device can be made differently.
  • the first plate is fixed to the second plate which forms part of the means for fixing the first plate to said part of the undercarriage. Fixing can be achieved by screwed, bolted, riveted or other elements.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
  • Elimination Of Static Electricity (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Description

La présente invention concerne le domaine de l'aéronautique et plus particulièrement les atterrisseurs d'aéronefs.The present invention relates to the field of aeronautics and more particularly to aircraft landing gear.

ETAT DE LA TECHNIQUESTATE OF THE ART

Le risque de foudroiement d'aéronef étant assez élevé, les aéronefs comprennent un certain nombre de moyens permettant de limiter les conséquences d'un impact de foudre. Les éléments structuraux de l'aéronef sont donc reliés à la masse de l'aéronef et les équipements susceptibles d'être foudroyés sont protégés par des paratonnerres. Les équipements actuellement installés sur les trains d'atterrissage ne sont pas menacés de sorte qu'il n'est pas prévu une quelconque protection contre la foudre.Since the risk of an aircraft being struck by lightning is quite high, aircraft include a certain number of means making it possible to limit the consequences of a lightning strike. The structural elements of the aircraft are therefore connected to the ground of the aircraft and the equipment liable to be struck by lightning is protected by lightning rods. The equipment currently installed on the landing gear is not threatened so that no protection against lightning is provided.

Par ailleurs, il existe depuis quelques années une volonté de réduction de la consommation de carburant et de la pollution produite par les moteurs d'avions. Pour atteindre cet objectif, des solutions alternatives ont été imaginées et développées pour déplacer les avions au sol sans l'aide des moteurs principaux qui sont gourmands en kérosène. L'un des concepts repose sur la fixation d'un motoréducteur électrique sur la jambe d'au moins l'un des atterrisseurs pour permettre à l'avion de se déplacer de manière autonome au sol sans recourir à ses moteurs principaux.In addition, for several years there has been a desire to reduce fuel consumption and the pollution produced by aircraft engines. To achieve this objective, alternative solutions have been devised and developed to move the aircraft on the ground without the help of the main engines which are greedy in kerosene. One of the concepts relies on the attachment of an electric gearmotor to the leg of at least one of the landing gears to allow the aircraft to move autonomously on the ground without using its main engines.

Il apparaît que le motoréducteur comporte des parties suffisamment écartées de la jambe de l'atterrisseur pour favoriser un effet de pointe de sorte que lesdites parties constitueraient des zones privilégiées d'impact de la foudre. Un tel foudroiement pourrait entraîner la destruction du motoréducteur et la transmission de forts courants et de hautes tensions vers les appareils électriques et/ou électroniques auxquels le motoréducteur est relié. Un risque d'incendie au niveau du fuselage n'est pas non plus à exclure.It appears that the geared motor has parts that are sufficiently spaced apart from the leg of the undercarriage to promote a peak effect so that said parts would constitute privileged lightning strike zones. Such a lightning strike could destroy the gear motor and transmit strong currents and high voltages to the electrical and/or electronic devices to which the gear motor is connected. A risk of fire in the fuselage cannot be ruled out either.

Il a été envisagé de dimensionner le blindage de l'ensemble du faisceau électrique de l'atterrisseur pour supporter l'onde de foudre. Cependant, quand bien même le blindage résisterait à l'onde de foudre, les courants induits par l'onde de foudre dans les conducteurs du faisceau électrique seraient encore trop importants pour les circuits électroniques de commande et notamment les calculateurs.Consideration was given to sizing the shielding of the entire lander electrical harness to withstand the lightning wave. However, even if the shielding resisted the lightning wave, the currents induced by the lightning wave in the conductors of the electrical harness would still be too high for the electronic control circuits and in particular the computers.

Il a également été envisagé de placer un paratonnerre sur l'atterrisseur, malheureusement les contraintes d'encombrement qui s'exercent dans cette zone de l'aéronef, en particulier lorsque le train est rentré dans sa soute, rendent très complexe la mise en place d'un tel paratonnerre.It has also been considered to place a lightning rod on the landing gear, unfortunately the space constraints which are exerted in this zone of the aircraft, in particular when the landing gear is returned to its hold, make the installation very complex. of such a lightning rod.

EP 2 735 850 A2 décrit une partie basse d'un atterrisseur d'aéronef comprenant un capteur agencé à l'intérieur d'une extrémité libre d'un essieu. Des doigts conducteurs s'étendent radialement depuis le capteur et sont en contact avec une surface interne de l'essieu pour former un chemin de faible impédance entre l'essieu et le capteur afin d'éviter la formation d'arc électriques dommageables dus par exemple à un foudroiement au niveau du nez de l'aéronef. EP 2 735 850 A2 describes a lower part of an aircraft landing gear comprising a sensor arranged inside a free end of an axle. Conductive fingers extend radially from the sensor and contact an inner surface of the axle to form a low impedance path between the axle and the sensor to prevent damaging arcing due to e.g. to a lightning strike at the nose of the aircraft.

OBJET DE L'INVENTIONOBJECT OF THE INVENTION

Un but de l'invention est de fournir un moyen pour limiter le risque qu'un foudroiement n'altère durablement le fonctionnement d'un aéronef.An object of the invention is to provide a means for limiting the risk that a lightning strike will permanently alter the operation of an aircraft.

BREF EXPOSE DE L'INVENTIONBRIEF DESCRIPTION OF THE INVENTION

A cet effet, on prévoit, selon l'invention, un atterrisseur d'aéronef, comprenant un équipement électrique fixé à une partie de l'atterrisseur et un dispositif anti-foudre comportant au moins un bouclier fixé à ladite partie de l'atterrisseur par des moyens de fixation pour s'étendre en regard de l'équipement électrique en une position écartée de ce dernier. Le bouclier comprenant au moins une première plaque en matériau électriquement conducteur agencée pour absorber une majeure partie d'une énergie thermique engendrée par un passage d'une onde de foudre et pour évacuer les charges électriques de l'onde de foudre.To this end, provision is made, according to the invention, for an aircraft undercarriage, comprising electrical equipment fixed to a part of the undercarriage and an anti-lightning device comprising at least one shield fixed to said part of the undercarriage by fastening means to extend facing the electrical equipment in a position spaced from the latter. The shield comprising at least a first plate made of electrically conductive material arranged to absorb a major part of a thermal energy generated by a passage of a lightning wave and to evacuate the electric charges of the lightning wave.

La première plaque est donc destinée à former le point d'entrée ou de sortie de l'onde de foudre et à évacuer le plus facilement possible les courants correspondants. La première phase de l'onde de foudre étant très puissante avec des fréquences très élevées, les courants ne rentrent pas dans la première plaque et circulent essentiellement à la surface de la première plaque. La seconde phase de l'onde de foudre est quant à elle très énergétique, les courants rentrent dans la plaque et la contrainte thermique est absorbée par la première plaque. La première plaque est de préférence en un matériau fusible à la température engendrée par le passage de l'onde de foudre de sorte qu'elle va fondre au moins en partie. La distance laissée entre la première plaque et l'équipement électrique permet de limiter le risque d'un échauffement excessif de l'équipement électrique.The first plate is therefore intended to form the point of entry or exit of the lightning wave and to evacuate the currents as easily as possible. correspondents. The first phase of the lightning wave being very powerful with very high frequencies, the currents do not enter the first plate and essentially circulate on the surface of the first plate. The second phase of the lightning wave is very energetic, the currents enter the plate and the thermal stress is absorbed by the first plate. The first plate is preferably made of a material that is fusible at the temperature generated by the passage of the lightning wave so that it will melt at least in part. The distance left between the first plate and the electrical equipment makes it possible to limit the risk of excessive heating of the electrical equipment.

De préférence, le dispositif anti-foudre comprend une deuxième plaque en matériau électriquement conducteur s'étendant parallèlement à la première plaque entre cette dernière et l'équipement électrique en une position écartée de l'équipement électrique et de la première plaque. Avantageusement, la première plaque est fixée sur la deuxième plaque qui forme une partie des moyens de fixation de la première plaque à ladite partie de l'atterrisseur, la deuxième plaque étant reliée à l'équipement électrique.Preferably, the anti-lightning device comprises a second plate of electrically conductive material extending parallel to the first plate between the latter and the electrical equipment in a position separated from the electrical equipment and the first plate. Advantageously, the first plate is fixed to the second plate which forms part of the means for fixing the first plate to said part of the undercarriage, the second plate being connected to the electrical equipment.

La deuxième plaque supporte la première plaque, assure la continuité des courants vers la structure de l'atterrisseur et constitue une seconde isolation thermique. Si la première plaque est en métal, la deuxième plaque bloque les éventuelles projections de métal en fusion provenant de la première plaque. L'équipement électrique est donc protégé des courants élevés, des projections de métal en fusion et de l'élévation de température localisée au point d'entrée ou de sortie de l'onde de foudre.The second plate supports the first plate, ensures the continuity of the currents towards the structure of the undercarriage and constitutes a second thermal insulation. If the first plate is made of metal, the second plate blocks any projections of molten metal coming from the first plate. The electrical equipment is therefore protected from high currents, splashes of molten metal and localized temperature rise at the point of entry or exit of the lightning wave.

L'invention a également pour objet un aéronef équipé d'un tel atterrisseur.The invention also relates to an aircraft equipped with such a landing gear.

D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description qui suit de modes de réalisation particuliers non limitatifs de l'invention.Other characteristics and advantages of the invention will become apparent on reading the following description of particular non-limiting embodiments of the invention.

BREVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF FIGURES

Il sera fait référence aux dessins annexés, parmi lesquels :

  • la figure 1 est une vue schématique en coupe transversale du dispositif anti-foudre selon l'invention ;
  • la figure 2 est une vue schématique en perspective d'un atterrisseur selon l'invention
  • la figure 3 est une vue schématique d'un aéronef équipé d'un tel atterrisseur.
Reference will be made to the attached drawings, among which:
  • the figure 1 is a schematic cross-sectional view of the anti-lightning device according to the invention;
  • the figure 2 is a schematic perspective view of a landing gear according to the invention
  • the picture 3 is a schematic view of an aircraft equipped with such a landing gear.

DESCRIPTION DETAILLEE DE L'INVENTIONDETAILED DESCRIPTION OF THE INVENTION

En référence aux figures, l'invention est décrite en application à un aéronef 50 comportant un fuselage 51 contenant une unité électronique de commande 52 de l'aéronef 50. Le fuselage 51 comprend un nez pourvu d'un atterrisseur généralement désigné en 100.With reference to the figures, the invention is described in application to an aircraft 50 comprising a fuselage 51 containing an electronic control unit 52 of the aircraft 50. The fuselage 51 comprises a nose provided with a landing gear generally designated 100.

L'atterrisseur 100 comprend une jambe 1 ayant une extrémité 1.1 articulée au fuselage 51 et une extrémité libre 1.2 pourvue de deux axes 101 pour recevoir chacun une roue 102. L'extrémité libre 1.2 est également pourvue d'un motoréducteur électrique 2 destiné à entraîner en rotation les roues 102 et relié par un faisceau 3 de câbles électriques à une source d'alimentation non représentée et à l'unité de commande 52. Le motoréducteur 2 est agencé pour engrener avec une roue dentée liée en rotation avec l'une des roues 102 de telle manière que le pilotage du motoréducteur 2 permette l'entraînement de la roue 102 en rotation lors des manœuvres de taxiage. Le faisceau 3 s'étend dans un chemin de câbles qui court le long de la jambe 1 de l'atterrisseur 100. L'atterrisseur 100 est connu en lui-même et ne sera pas plus détaillé ici. En particulier, les moyens de déploiement et rétraction de l'atterrisseur 100 ne sont pas représentés, de même que les moyens permettant d'engager le motoréducteur sur la roue dentée et de l'en dégager.The undercarriage 100 comprises a leg 1 having an end 1.1 hinged to the fuselage 51 and a free end 1.2 provided with two axles 101 each to receive a wheel 102. The free end 1.2 is also provided with an electric gear motor 2 intended to drive in rotation the wheels 102 and connected by a harness 3 of electric cables to a power source, not shown, and to the control unit 52. The geared motor 2 is arranged to mesh with a toothed wheel connected in rotation with one of the wheels 102 in such a way that the control of the geared motor 2 allows the driving of the wheel 102 in rotation during taxiage maneuvers. The harness 3 extends in a cable tray which runs along the leg 1 of the undercarriage 100. The undercarriage 100 is known in itself and will not be further detailed. here. In particular, the deployment and retraction means of the undercarriage 100 are not shown, nor are the means for engaging the geared motor on the toothed wheel and disengaging it therefrom.

L'atterrisseur 100 comprend un dispositif anti-foudre, généralement désigné en 10, comportant plusieurs boucliers fixés à l'extrémité libre 1.2 de la jambe 1 de l'atterrisseur par des moyens de fixation de telle manière que les boucliers s'étendent en regard du motoréducteur 2 et du tronçon inférieur du faisceau 3. Chaque bouclier s'étend en une position écartée du motoréducteur 2 ou du tronçon inférieur du faisceau 3 en regard duquel il est positionné.The lander 100 comprises an anti-lightning device, generally designated at 10, comprising several shields fixed to the free end 1.2 of the leg 1 of the lander by fastening means in such a way that the shields extend opposite of the geared motor 2 and of the lower section of the beam 3. Each shield extends in a spaced position from the geared motor 2 or from the lower section of the beam 3 opposite which it is positioned.

Chaque bouclier comprend une première plaque 11 et une deuxième plaque 12.Each shield comprises a first plate 11 and a second plate 12.

La première plaque 11 est en matériau électriquement conducteur et est agencée pour absorber une majeure partie d'une énergie thermique engendrée par un passage d'une onde de foudre et pour évacuer les charges électriques de l'onde de foudre. La première plaque 11 est en métal et a une épaisseur comprise entre 2 et 4 mm environ. Le métal de la première plaque 11 est ici un aluminium.The first plate 11 is made of electrically conductive material and is arranged to absorb a major part of a thermal energy generated by a passage of a lightning wave and to evacuate the electric charges of the lightning wave. The first plate 11 is made of metal and has a thickness between approximately 2 and 4 mm. The metal of the first plate 11 is here an aluminum.

La deuxième plaque 12 est en matériau électriquement conducteur. La deuxième plaque 12 est en métal et a une épaisseur comprise entre 1 et 2 mm environ. Le métal de la deuxième plaque 12 est ici un aluminium ou un acier.The second plate 12 is made of electrically conductive material. The second plate 12 is made of metal and has a thickness between approximately 1 and 2 mm. The metal of the second plate 12 is here an aluminum or a steel.

Sur la figure 1, on voit que la première plaque 11 est fixée par des colonnes sur la deuxième plaque 12 qui forme une partie des moyens de fixation de la première plaque 11 à l'extrémité libre 1.2 de la jambe 1 de l'atterrisseur. Ces colonnes sont formées chacune d'un boulon en acier ou en aluminium s'étendant dans une entretoise tubulaire qui est serrée entre les deux plaques pour les maintenir écartées les deux plaques l'une de l'autre. La deuxième plaque 12 s'étend parallèlement à la première plaque 11 entre cette dernière et le motoréducteur 2 et le faisceau 3 en une position écartée du motoréducteur 2 et du faisceau 3 et de la première plaque 11. La première plaque 11 est séparée de la deuxième plaque 12 d'une distance comprise entre 3 mm et 5 mm environ.On the figure 1 , we see that the first plate 11 is fixed by columns on the second plate 12 which forms part of the means for fixing the first plate 11 to the free end 1.2 of the leg 1 of the undercarriage. These columns are each formed of a steel or aluminum bolt extending into a tubular spacer which is clamped between the two plates to hold them apart the two plates from each other. The second plate 12 extends parallel to the first plate 11 between the latter and the geared motor 2 and the beam 3 in a spaced position from the geared motor 2 and from the beam 3 and from the first plate 11. The first plate 11 is separated from the second plate 12 by a distance between approximately 3 mm and 5 mm.

Les moyens de fixation des boucliers s'étendant en regard du faisceau 3 relient la deuxième plaque 12 au chemin de câbles par des colonnes. Ces colonnes sont formées chacune d'un boulon en acier ou en aluminium s'étendant dans une entretoise tubulaire maintenant écartés la deuxième plaque et le chemin de câbles.The means for fixing the shields extending opposite the bundle 3 connect the second plate 12 to the cable tray by columns. These columns are each formed of a steel or aluminum bolt extending in a tubular spacer holding apart the second plate and the cable tray.

Les moyens de fixation des boucliers s'étendant en regard du motoréducteur 2 comportent ici également deux parois latérales 13, 14 en matériau électriquement conducteur qui relient la deuxième plaque 12 à l'extrémité libre 1.2 et s'étendent de part et d'autre du motoréducteur 2 à distance de celui-ci.The means for fixing the shields extending opposite the geared motor 2 here also comprise two side walls 13, 14 made of electrically conductive material which connect the second plate 12 to the free end 1.2 and extend on either side of the gearmotor 2 at a distance from it.

Bien entendu, l'invention n'est pas limitée aux modes de réalisation décrits mais englobe toute variante entrant dans le champ de l'invention telle que définie par les revendications.Of course, the invention is not limited to the embodiments described but encompasses any variant falling within the scope of the invention as defined by the claims.

En particulier, le bouclier peut ne comprendre qu'une seule plaque, à savoir la première plaque. La première plaque aura alors une épaisseur plus importante pour pouvoir absorber l'énergie thermique engendrée par le passage de l'onde de foudre. Ceci est particulièrement important dans le cas où la première plaque est en métal : il faut éviter que la première plaque soit transpercée et que du métal en fusion soit projeté sur l'équipement électrique.In particular, the shield may only comprise a single plate, namely the first plate. The first plate will then have a greater thickness in order to be able to absorb the thermal energy generated by the passage of the lightning wave. This is particularly important in the case where the first plate is made of metal: it is necessary to prevent the first plate from being pierced and molten metal from being projected onto the electrical equipment.

L'équipement électrique peut être tout élément conduisant l'électricité, un faisceau électrique, un actionneur électromagnétique ou électromécanique, un circuit de puissance ou un circuit de commande...Electrical equipment can be any item that conducts electricity, an electrical harness, a electromagnetic or electromechanical actuator, a power circuit or a control circuit...

Les parois latérales 13, 14 peuvent être pourvues de lumières pour permettre une circulation d'air favorisant un refroidissement des équipements électriques.The side walls 13, 14 can be provided with openings to allow air circulation promoting cooling of the electrical equipment.

Le bouclier peut être installé sur tout type de train et par exemple sur un train à deux rues ou sur un train bogie à quatre ou six roues.The shield can be installed on any type of train and for example on a two-street train or on a bogie train with four or six wheels.

L'actionneur et la liaison à la roue du dispositif de taxiage peuvent être réalisés différemment.The actuator and the connection to the wheel of the taxiing device can be made differently.

La première plaque est fixée sur la deuxième plaque qui forme une partie des moyens de fixation de la première plaque à ladite partie de l'atterrisseur. La fixation peut être réalisée par des éléments vissés, boulonnés, rivetés ou autre.The first plate is fixed to the second plate which forms part of the means for fixing the first plate to said part of the undercarriage. Fixing can be achieved by screwed, bolted, riveted or other elements.

Claims (12)

  1. An aircraft undercarriage including electrical equipment (2, 3) fastened to a portion (1) of the undercarriage and a lightning protection device (10) comprising at least one shield fastened to said portion (1) of the undercarriage by fastener means so as to extend in register with the electrical equipment (2, 3) in a position that is spaced apart therefrom, the shield comprising at least a first plate (11) made of electrically conductive material that is arranged to absorb a major portion of the heat energy that is generated by the passage of a lightning wave and to discharge the electric charge of the lightning wave.
  2. An undercarriage according to claim 1, wherein the lightning protection device (10) further comprises a second plate (12) made of electrically conductive material extending parallel to the first plate (11) between the first plate and the electrical equipment (2, 3) in a position that is spaced apart from the electrical equipment (2, 3) and from the first plate (11), the first plate (11) being fastened on the second plate (12), which forms a portion of the means for fastening the first plate (11) to said portion (1) of the undercarriage, the second plate (12) being connected to the electrical equipment.
  3. An undercarriage according to claim 2, wherein the first plate (11) is spaced apart from the second plate (12) by a distance lying in the range 3 mm to 10 mm approximately, and preferably in the range 3 mm to 5 mm.
  4. An undercarriage according to claim 2 or claim 3, wherein the first plate (11) is made of metal and has thickness lying in the range 2 mm to 4 mm approximately.
  5. An undercarriage according to claim 4, wherein the metal of the first plate (11) is an aluminum alloy.
  6. An undercarriage according to any one of claims 2 to 5, wherein the second plate (12) is made of metal and has thickness lying in the range 1 mm to 4 mm approximately, and preferably in the range 1 mm to 2 mm.
  7. An undercarriage according to claim 6, wherein the metal of the second plate (12) is an aluminum alloy.
  8. An undercarriage according to claim 6, wherein the metal of the second plate (12) is a steel.
  9. An undercarriage according to any preceding claim, wherein the electrical equipment is an electrical harness (3) .
  10. An undercarriage according to any preceding claim, wherein the electrical equipment is an electromagnetic actuator (2) such as a gear motor.
  11. An undercarriage according to any one of claims 2 to 8, wherein the fastener means include two side walls (13, 14) made of electrically conductive material that extend on either side of the electrical equipment (2, 3) at a distance therefrom and that are connected to the second plate (12).
  12. An aircraft including a fuselage containing a cockpit provided with an electronic control unit, the fuselage being provided with at least one undercarriage according to any preceding claim, the electrical equipment of the undercarriage being connected to the electronic control unit.
EP19170692.8A 2018-04-26 2019-04-23 Undercarriage provided with a lithgning protection device Active EP3560827B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1853668A FR3080604B1 (en) 2018-04-26 2018-04-26 LANDER WITH LIGHTNING DEVICE

Publications (2)

Publication Number Publication Date
EP3560827A1 EP3560827A1 (en) 2019-10-30
EP3560827B1 true EP3560827B1 (en) 2022-06-01

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US (1) US11554878B2 (en)
EP (1) EP3560827B1 (en)
CN (1) CN110406662B (en)
CA (1) CA3040557C (en)
ES (1) ES2923548T3 (en)
FR (1) FR3080604B1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3110544B1 (en) * 2020-05-20 2022-06-17 Safran Landing Systems Landing gear fitted with lightning protection
CN118025487B (en) * 2024-04-12 2024-06-14 西安爱邦电磁技术有限责任公司 Lightning protection lightning receiving equipment for multi-rotor unmanned aerial vehicle

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2320547A (en) * 1942-01-30 1943-06-01 Roy L Tiger Landing wheel rotating device for airplanes
AU2002235117A1 (en) * 2000-08-18 2002-05-15 Goodrich Corporation Aircraft drainmast assembly with lightning protection
US7954757B2 (en) 2004-03-29 2011-06-07 Goodrich Corporation Landing gear noise attenuation
US8814587B2 (en) * 2012-11-27 2014-08-26 Goodrich Corporation Low impedance equipment interface
US10933981B2 (en) 2016-06-21 2021-03-02 Goodrich Corporation Aerodynamic noise reducing thin-skin landing gear structures and manufacturing techniques

Also Published As

Publication number Publication date
CN110406662B (en) 2024-01-02
EP3560827A1 (en) 2019-10-30
FR3080604B1 (en) 2020-04-17
ES2923548T3 (en) 2022-09-28
CA3040557A1 (en) 2019-10-26
US11554878B2 (en) 2023-01-17
CN110406662A (en) 2019-11-05
US20190329902A1 (en) 2019-10-31
FR3080604A1 (en) 2019-11-01
CA3040557C (en) 2021-04-27

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